Abstract

The developments of highly maneuverable aircraft have prompted the extensive studies of the flow past a delta wing. The most distinguishing feature of the delta wing flow field is the existence of a pair of well organized and highly energetic leading edge vortices, formed at moderate attack as a result of the flow separation along the two sharp leading edges. The leading edge vortices induce large suction force on the delta wing surface and receive significant amount of attention because of their Importance to the aerodynamics of the aircraft. To understand the flow over compound delta wing, this report has been made to study the various flow field associated over the delta wing with variation of Reynolds number, Mach number, aspect ratio, sideslip, leading edge shape and sweep angle.